NACA 0010-34 (naca001034-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: NACA 0010-34 (naca001034-il) Reynolds number: 200,000 Max Cl/Cd: 38.57 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca001034-il-200000-n5.txt Download as CSV file: xf-naca001034-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0010-34
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.6329 0.09017 0.08675 -0.0204 1.0000 0.0100
-10.000 -0.6425 0.08180 0.07838 -0.0271 1.0000 0.0095
-9.750 -0.6575 0.07483 0.07135 -0.0324 1.0000 0.0092
-9.500 -0.6746 0.06950 0.06593 -0.0348 1.0000 0.0089
-9.250 -0.6919 0.06523 0.06156 -0.0347 1.0000 0.0087
-9.000 -0.7082 0.06172 0.05792 -0.0326 1.0000 0.0086
-8.750 -0.7193 0.05814 0.05417 -0.0302 1.0000 0.0087
-8.500 -0.7261 0.05460 0.05044 -0.0276 1.0000 0.0088
-8.250 -0.7296 0.05122 0.04684 -0.0248 1.0000 0.0091
-8.000 -0.7306 0.04798 0.04335 -0.0216 1.0000 0.0094
-7.750 -0.7304 0.04482 0.03992 -0.0181 1.0000 0.0096
-7.500 -0.7291 0.04165 0.03645 -0.0145 1.0000 0.0096
-7.250 -0.7264 0.03845 0.03293 -0.0108 1.0000 0.0095
-7.000 -0.7211 0.03541 0.02954 -0.0072 1.0000 0.0093
-6.750 -0.7131 0.03256 0.02628 -0.0037 1.0000 0.0093
-6.500 -0.7022 0.02994 0.02328 -0.0006 1.0000 0.0092
-6.250 -0.6885 0.02757 0.02055 0.0022 1.0000 0.0093
-6.000 -0.6723 0.02546 0.01811 0.0045 1.0000 0.0095
-5.750 -0.6542 0.02361 0.01597 0.0066 1.0000 0.0098
-5.500 -0.6351 0.02208 0.01422 0.0084 1.0000 0.0103
-5.250 -0.6158 0.02145 0.01343 0.0100 1.0000 0.0113
-5.000 -0.5986 0.01911 0.01093 0.0121 1.0000 0.0125
-4.750 -0.5724 0.01771 0.00944 0.0121 0.9979 0.0135
-4.500 -0.5432 0.01664 0.00823 0.0114 0.9952 0.0151
-4.250 -0.5136 0.01589 0.00737 0.0107 0.9919 0.0184
-4.000 -0.4833 0.01511 0.00641 0.0098 0.9886 0.0217
-3.750 -0.4523 0.01441 0.00565 0.0088 0.9856 0.0330
-3.500 -0.4268 0.01319 0.00491 0.0085 0.9812 0.1335
-3.250 -0.4060 0.01130 0.00434 0.0084 0.9776 0.4241
-3.000 -0.3892 0.01010 0.00428 0.0106 0.9723 0.6597
-2.750 -0.3612 0.00988 0.00437 0.0110 0.9687 0.7559
-2.500 -0.3276 0.00986 0.00435 0.0101 0.9661 0.7949
-2.250 -0.2983 0.00985 0.00427 0.0098 0.9607 0.8154
-2.000 -0.2649 0.00986 0.00422 0.0087 0.9569 0.8326
-1.750 -0.2292 0.00988 0.00415 0.0071 0.9540 0.8470
-1.500 -0.1984 0.00989 0.00411 0.0065 0.9486 0.8598
-1.250 -0.1660 0.00989 0.00407 0.0055 0.9435 0.8714
-1.000 -0.1301 0.00990 0.00402 0.0038 0.9399 0.8808
-0.750 -0.0991 0.00992 0.00401 0.0032 0.9332 0.8898
-0.500 -0.0660 0.00990 0.00397 0.0021 0.9276 0.8989
-0.250 -0.0327 0.00992 0.00397 0.0010 0.9209 0.9061
0.000 0.0000 0.00991 0.00395 0.0000 0.9140 0.9140
0.250 0.0328 0.00992 0.00397 -0.0010 0.9061 0.9209
0.500 0.0661 0.00990 0.00397 -0.0021 0.8989 0.9276
0.750 0.0992 0.00992 0.00401 -0.0032 0.8898 0.9332
1.000 0.1302 0.00990 0.00402 -0.0038 0.8808 0.9399
1.250 0.1661 0.00989 0.00406 -0.0055 0.8714 0.9435
1.500 0.1984 0.00989 0.00411 -0.0065 0.8598 0.9487
1.750 0.2293 0.00987 0.00415 -0.0071 0.8470 0.9540
2.000 0.2649 0.00986 0.00422 -0.0087 0.8326 0.9570
2.250 0.2984 0.00985 0.00426 -0.0098 0.8154 0.9608
2.500 0.3277 0.00986 0.00435 -0.0101 0.7950 0.9661
2.750 0.3612 0.00987 0.00437 -0.0110 0.7558 0.9687
3.000 0.3892 0.01009 0.00427 -0.0106 0.6601 0.9723
3.250 0.4060 0.01130 0.00433 -0.0084 0.4241 0.9776
3.750 0.4523 0.01442 0.00565 -0.0088 0.0329 0.9857
4.000 0.4834 0.01510 0.00641 -0.0099 0.0218 0.9886
4.250 0.5137 0.01589 0.00737 -0.0107 0.0185 0.9919
4.500 0.5434 0.01664 0.00823 -0.0115 0.0151 0.9953
4.750 0.5726 0.01771 0.00944 -0.0121 0.0135 0.9979
5.000 0.5984 0.01911 0.01093 -0.0120 0.0125 1.0000
5.250 0.6157 0.02149 0.01347 -0.0100 0.0112 1.0000
5.500 0.6350 0.02209 0.01422 -0.0084 0.0103 1.0000
5.750 0.6541 0.02360 0.01596 -0.0066 0.0098 1.0000
6.000 0.6722 0.02545 0.01810 -0.0045 0.0095 1.0000
6.250 0.6884 0.02756 0.02054 -0.0021 0.0093 1.0000
6.500 0.7021 0.02993 0.02327 0.0006 0.0092 1.0000
6.750 0.7130 0.03256 0.02627 0.0038 0.0093 1.0000
7.000 0.7210 0.03541 0.02954 0.0072 0.0093 1.0000
7.250 0.7263 0.03845 0.03293 0.0108 0.0095 1.0000
7.500 0.7291 0.04165 0.03645 0.0145 0.0096 1.0000
7.750 0.7304 0.04482 0.03992 0.0181 0.0096 1.0000
8.000 0.7309 0.04797 0.04334 0.0216 0.0094 1.0000
8.250 0.7298 0.05121 0.04683 0.0247 0.0091 1.0000
8.500 0.7265 0.05458 0.05042 0.0276 0.0088 1.0000
8.750 0.7196 0.05814 0.05417 0.0301 0.0086 1.0000
9.000 0.7084 0.06176 0.05796 0.0325 0.0087 1.0000
9.250 0.6922 0.06529 0.06162 0.0346 0.0087 1.0000
9.500 0.6751 0.06955 0.06599 0.0347 0.0089 1.0000
9.750 0.6582 0.07491 0.07143 0.0322 0.0091 1.0000
10.000 0.6432 0.08194 0.07853 0.0268 0.0095 1.0000
10.250 0.6342 0.09034 0.08692 0.0200 0.0099 1.0000
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Polar data table (+)
Polar graphs
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